2007-05-17: Airworthiness Limitations Section (ALS)

2007-05-17 Pratt & Whitney: Amendment 39-14978. Docket No. FAA-2007- 27023; Directorate Identifier 98-ANE-47-AD. Effective Date (a) This airworthiness directive (AD) becomes effective April 12, 2007. Affected ADs (b) This AD supersedes AD 2002-08-11, Amendment 39-12719. Applicability (c) This AD applies to Pratt & Whitney (PW) JT9D-3A, -7, -7A, - 7H, -7AH, -7F, -7J, -20J, -59A, -70A, -7Q, -7Q3, -7R4D, -7R4D1, - 7R4E, -7R4E1, -7R4E4, -7R4G2, and -7R4H1 series turbofan engines. These engines are installed on, but not limited to, Boeing 747 and 767 series, McDonnell Douglas DC-10 series, and Airbus Industrie A300 and A310 series airplanes. Unsafe Condition (d) This AD results from the need to require enhanced inspection of selected critical life-limited parts of JT9D series turbofan engines. We are issuing this AD to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. (f) Within the next 180 days after the effective date of this AD, revise the manufacturer's Instructions for Continued Airworthiness Limitations Section (ALS), and for air carrier operations revise the approved continuous airworthiness maintenance program by adding the following: Mandatory Inspections (1) Perform inspections of the following parts at each piece- part opportunity in accordance with the instructions provided in the applicable manual provisions: Engine Model Engine Manual Part Number (P/N) Part Nomenclature Inspect per Manual Section Inspection/Check All Fan Hubs 72-31-04 Inspection-02 All HPC Stage 5 15 Disks and Rear Compressor Drive Turbine Shafts 72-35-00 Inspection-03 All HPT Stage 1-2 Disks and Hubs 72-51-00 Inspection-03 All HPT Stage2 Disk Web Tie-rod Holes 72-51-02 Inspection- 05 3A/7/7A/7AH/7F/7H/7J/20/ 20J *646028 (or the equivalent customized versions, 770407 and 770408) All LPT Stage 3 6 Disks and Hubs 72-52-00 Inspection-03 All Fan Hubs 72-31-00 Check-00 All HPC Stage 5 15 Disks and Rear Compressor Drive Turbine Shafts 72-35-00 Check-00 All HPT Stage 1-2 Disks and Hubs 72-51-00 Check-03 All HPT Stage 1 Disk Web Cooling Holes 72-51-02 Check-03 59A/70A 754459 All LPT Stage 3 6 Disks and Hubs 72-52-00 Check-03 All Fan Hubs 72-31-00 Inspection-03 All HPC Stage 5 15 Disks and Rear Compressor Drive Turbine Shafts 72-35-00 Inspection-03 All HPT Stage 1-2 Disks and Hubs All HPT Stage 1 Disk Web Cooling Holes 72-51-00 72-51-06 Inspection-03 Inspection-03 7Q/7Q3 777210 All LPT Stage 3 6 Disks and Hubs 72-52-00 Inspection-03 All Fan Hubs 72-31-00 Inspection/Check-03 All HPC Stage 5 15 Disks and Rear Compressor Drive TurbineShafts 72-35-00 Inspection/Check 03 All HPT Stage 1-2 Disks and Hubs 72-51-00 Inspection/Check 03 7R4 ALL 785058, 785059, and 789328 All LPT Stage 3 6 Disks and Hubs 72-52-00 Inspection/Check 03 7R4D/D1/E/E1 785058 and 785059 All HPT Stage 1 Disk Web Cooling Holes 72-51-06 Inspection/Check-02 * P/N 770407 and 770408 are customized versions of P/N 646028 engine manual. (2) For the purposes of these mandatory inspections, piece-part opportunity means: (i) The part is considered completely disassembled when done in accordance with the disassembly instructions in the manufacturer's engine manual; and (ii) The part has accumulated more than 100 cycles-in-service since the last piece-part opportunity inspection, provided that the part was not damaged or related to the cause for its removal from the engine.'' Alternative Methods of Compliance (g) You must perform these mandatory inspections using the ALS of the Instructions for Continued Airworthiness and the applicable Engine Manual unless you receive approval to use an alternative method of compliance under paragraph (h) of this AD. Section 43.16 of the Federal Aviation Regulations (14 CFR 43.16) may not be used to approve alternative methods of compliance or adjustments to the times in which these inspections must be performed. (h) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Maintaining Records of the Mandatory Inspections (i) You have met the requirements of this AD when you change the manufacturer's Instructions for Continued Airworthiness ALS specified in paragraph (f) of this AD. For air carriers operating under part 121 of the Federal Aviation Regulations (14 CFR part 121), you have met the requirements of this AD when you modify your continuous airworthiness maintenance plan to reflect those changes. You do not need to recordeach piece-part inspection as compliance to this AD but you must maintain records of those inspections according to the regulations governing your operation. For air carriers operating under part 121, you may use either the system established to comply with section 121.369 or an alternative accepted by your principal maintenance inspector if that alternative: (1) Includes a method for preserving and retrieving the records of the inspections resulting from this AD; and (2) Meets the requirements of section 121.369(c); and (3) Maintains the records either indefinitely or until the work is repeated. (j) These record keeping requirements apply only to the records used to document the mandatory inspections required as a result of revising the ALS of the Instructions for Continued Airworthiness as specified in paragraph (f) of this AD. These record keeping requirements do not alter or amend the record keeping requirements for any other AD or regulatory requirement. Related Information (k) Contact Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238-7758, fax (781) 238-7199; e-mail: mark.riley@faa.gov for more information about this AD.